Aeroplane.



.9. WLBOYEA.

- AEROPLANE.

APPLICA-T-ION FILED JAN. I5, 918.

Patented Apr. 1, 1919.

3 SHEETS-SHEET I.

0. W. BOYEA.

AEROPLANE.

APPLICATION FILED JAN-15,1918.

1 ,299, 1 1 1., Patented Apr. 1, 1919.

3 SHEETSSHEEI' 3.

WITNESSES v IIWE/VTOR ATTORNEYS OVILA w. BOYEA, or BARRE, VERMONT.

AEROPLANE.

Specification of Letters Patent.

Patented Apr. 1, an.

Application filedJanuary 15, 1918. Serial No. 211,924.

To all whom it may concern:

Be it known that I, OVILA W. BOYEA, a citizen of the United States, and a resident of Barre, in the county of Washington and State of Vermont, have invented a new and Improved Aeroplane, of which the following is a full, clear, and exact description.

Among the principal objects which the present invention-has in view. are: to increase the propelling feature of the driving mechanism with which the aeroplane is provided; to increase the levitation of the aeroplane; to regulate the flight, and to check the flight of the aeroplane.

Drawings.

Fig. 3 is a horizontal section, the section being taken as on the line 3-3 in Fig. 2;

Fig. 4 is a front elevation of the aeroplane;

Fig. 5 is a vertical cross section, thesection being taken as on the line 5-5 in Fig. 2.

Description.

frame 12 and a central stanchion 13. The

stanchion 13, as seen best in Fig. 2, forms a central support for a tie brace 14, On which is mounted a bearing box 15 for the main driving shaft 16. The shaft 16 is extended lengthwise of the aeroplane in a line parallel with the longitudinal axis thereof. It is supported by a second U-shaped frame 17, best shown in Fig. 4 of the drawings, and bya cross brace 18 connected therewith. The driving shaft 16 is provided with a mitered gear wheel 19.

At the opposite ends of the shaft 16, are mounted propellers 20 and 21. The propellers 20 and 21" are preferably of equal size and pitch. The shaft 16 is operatively connected with a motor 22, by means of a sprocket chain .23, said shaft being supported adjacent its rear end by a cross brace 24. The brace 24 is carried on stanchions 25, whichsupport the deck 26.

The deck 27' and an overhang 28 meet at the forward ends of the aeroplane to form a cutting edge 29, by which the air is divided, part to be lifted and part to be depressed. The deck 27 and overhang 28 have triangular receding sections 30 and 31. The forward edges of the deck 27 overhang 28, and sections 30 and 31 converge, as shown best in Figs. 1 and 4 of the drawings. These planes form at the rear thereof, a space and chamber triangular in cross section. The upper and lower decks are prevented from collapsing by thin braces 32.

At the rear of the extreme end of the chamber thus formed, the main carrying planes of the aeroplane are located. The carrying planes referred to each comprise two sections, to wit', the solid section33, and a rear section, embodying a series of closelyfitting slats 34. The slats 34 are pivotally mounted on rails 35, downwardly and rearwardly curved, as shown best in Fig. 2 of the drawings. The slats 34 are pivoted at the rear of each slat. All of the slats are connected by a framework 36 and a link 37 to a lever 38, the handle 39 whereof is adjacent the drivers seat 40.

"As shown best in Figs. 3 and 5, a straight passageway is formed over the top of the fuselage of the machine and between the carrying planes 33 and sets of slats 34. It is through this passageway that the propellers 20 and 21 operate.

In line with the above-mentioned passageway and adjacent the controlling rudders of the machine, are pivotally mounted vertical slats 41. The slats 41 are operatively connected by pivotally operating rods 42, the ends whereof are connected with bell crank levers 43 at opposite sides of the machine. The long ends of the levers 43 are connected by means of rods 44, with operating levers 45. The levers 45, as seen best in Figs. 2 and 5 of the drawings, are disposed. adjacent the drivers seat 40.

The slats 41 may be simultaneously or independently operated to open and close. When closed, the passageway above referred to as extending lengthwise of the machine, is virtually closed or an abutment is formed by which the air is pocketed to form a drag or anchor for the machine. It is obvious that if one set of slats 41 is permitted to remain open while the opposite set is closed,

f ll

the closed set will form a drag at one side of the vertical longitudinal plane of the machine, thereby operating as a rudder. Tn operating the machine, this aid is often taken advantage of.

At the rear of the slats 41, are disposed. the horizontal rudder 46 and the climbing and diving rudders 47. As best shown in Fig. 2 of the drawings, there are two rudders 47. The rudder 46 has cutaway or inclined end edges 48 for permitting the lift and depression of the rudders 417. The rudders46 and 47 are operated by any of the conventional forms of mechanisms furnished. V.

The wheel 19 on the shaft 16 is operatively engaged with a gear wheel 49. The gear Wheel 49 is fixedly mounted on a shaft 50, which shaft extends transverse the aero plane. As seen best in Figs. 3 and 5, the shaft 50 has permanently mounted thereon two propellers. As seen best in 2, the propellers are provided with cupped blades 51. The shaft 50 is mounted in bearings which hold the shaft at approximately the level of the lower edge of the overhang 28, Which serves to protect or shelter the upper portions of said propellers, or to shelter the blades 51 when extended above the horizontal center of the shaft 50.

In consequence of this arrangement, the propellers and blades 51 thereof serve to press the air with which they are brought into contact, downward and rearward, thus forming auxiliary levitating and propelling means.

To operate an aeroplane when constructed and arrangedin accordance with the present invention, the motor 22 is started and the power generated thereby is transmitted by means of the chain 23, to the shaft '16. The propellers 20 and 21 are rotated with equal effect to propel the machine in a forward direction. Through the intermediary of the gear wheels 19 and 49, the shaft 50 with the propellers at the lateral extremes thereof, is rotated. The operation of the blades 5i of the propellers, as above stated, is to grip the air and press the same backward with the resulting effect that the aeroplane is moved forward, the operation being in unison with the operation of the propellers 20 and 21. In other words, the power mecha nism with which the aeroplane is provided is distributed at four points, thereby steadying the operation of the driving mechanism and the action of the aeroplane. As the operation of the blades 51 of the propellers mounted on the shaft 50, is to depress the air, the blades serve to stabilize the action of the aeroplane in its flight.

During the flight of the machine, it will be observed that when the same is held steady in its forward course, the wedgeshaped construction produced by the declr it chine as the praslures produced cllned surf of said equalized, i

le or deflected to ch: 4 be seen that the Q angle incidenc pressure t. ll he o lower docks in correspond nee of the aeroplane to elimh or dive. will be seen that the med s-shape const tion automatically s itself to the direction of flight, and as soon as the s becomes established, assists in. stahiliain direction of flight.

The normal levitation of the'aeroplar s supported by the operation of the blade and the depressed sections formed slats ill at the of the slat sections lit will he noted that as the air is deli real vardly from the blades 51, it imp upon the 3d, which, if closed, sections that escort a levitating or up gliding effect, thereby assisting in 11 i the aeroplane. i

It is obvious that if the aviator desir to alter the lifting power of sec formed by the slats 34;, he accomplishes by manipulating the le' s 39 to open at close the said T slats, the air pressure on posed thereby, is relieved.

During the normal l of the aeropla the slats ll at the tilt of the machine maintained open. she n in the If it is desired to machine as wl a, a landing, aviator by oper 1e levers d5, closes t slat-s ll, with the sheet of producing a so wall perpendicular to the line of flight, which serves as a drag on the air. It will he noted that the action of the construction formed by the slats l? may he modified by completely or partially I said slats While the operatic I the sections formed ployed to assist in land employed for checl' machine in midair to i for maneuvering as wh em tary M06, as a help t the Y eyed in 1 l urther, the may he sustain the machine or d" descent the planes, I depressed tective structure d o sections; and means tor anee of said inclined fi. An aeroplane comprising a plurality of carrying planes, said planes having rearwardly-depressed inclined sections; a protective structure disposed above said inclined sections; and means for varying the resistance of said inclined sections, said means embodying a plurality of slats pivotally mounted for closing one upon the other to produce a solid wall, and a controlling mechanism operated manually and l1av- 10 ing a hand lever contiguous to the seat of the driver of the aeroplane for roc ing said slats on their pivots. OVILA. \V. BOYEA. 

